EP2041494B1 - Gas turbine engine premix injectors - Google Patents
Gas turbine engine premix injectors Download PDFInfo
- Publication number
- EP2041494B1 EP2041494B1 EP06850471.1A EP06850471A EP2041494B1 EP 2041494 B1 EP2041494 B1 EP 2041494B1 EP 06850471 A EP06850471 A EP 06850471A EP 2041494 B1 EP2041494 B1 EP 2041494B1
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- EP
- European Patent Office
- Prior art keywords
- injector
- mixing duct
- fuel
- air
- slots
- Prior art date
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- 239000000446 fuel Substances 0.000 claims description 113
- 238000002156 mixing Methods 0.000 claims description 48
- 239000007788 liquid Substances 0.000 claims description 33
- 238000002485 combustion reaction Methods 0.000 claims description 24
- 239000000203 mixture Substances 0.000 claims description 12
- 239000012530 fluid Substances 0.000 claims description 5
- 238000004891 communication Methods 0.000 claims description 3
- 239000007789 gas Substances 0.000 description 24
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 238000000889 atomisation Methods 0.000 description 1
- 230000004323 axial length Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 239000003344 environmental pollutant Substances 0.000 description 1
- 230000004907 flux Effects 0.000 description 1
- 230000006870 function Effects 0.000 description 1
- 229930195733 hydrocarbon Natural products 0.000 description 1
- 150000002430 hydrocarbons Chemical class 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 239000003350 kerosene Substances 0.000 description 1
- 239000003345 natural gas Substances 0.000 description 1
- 231100000719 pollutant Toxicity 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
- 238000005086 pumping Methods 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/34—Feeding into different combustion zones
- F23R3/346—Feeding into different combustion zones for staged combustion
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
- F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/36—Supply of different fuels
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- the technical field relates generally to gas turbine engine fuel injectors, and more particularly, but not exclusively, to premix injectors for industrial gas turbine engines.
- Gas turbine engines are an efficient source of useful energy and have proven reliable for electricity generation, as well as for other uses.
- Gas turbine engines may include premix injectors for providing a mixture of air and fuel for combustion.
- Many gas turbine engine premix injectors suffer from a number limitations, and drawbacks, for example, those respecting size, complexity, part commit, emissions, and others. Thus, there is a need for the unique and inventive premix injectors disclosed herein.
- EP1321715 discloses an improved combination of a premixing chamber and a combustion chamber, with low emission of pollutants, for gas turbines running on liquid and/or gas fuel, in which the combustion chamber has a truncated conical end a and is surrounded by a cavity for cooling air, the cavity carrying combustion air to the premixing chamber, which has at its inlet apertures or ports which can be constricted according to the quantity of fuel used, and at its outlet a circumferential set of burners to create a corresponding set of additional flames.
- Gas fuel supply means and liquid fuel injection devices are provided in the premixing chamber, and a set of liquid fuel injectors is present on the end.
- FIG. 1 there is illustrated an industrial gas turbine engine 10, including, an inlet 12, a compressor section 14, a combustor section 16, a turbine section 18, a power turbine section 20 and an exhaust 22.
- Turbine section 18 is arranged to drive the compressor section 14 and power turbine section 20 drives an electrical generator 26 via a shaft 24.
- power turbine section 20 may be arranged to provide drive for other applications.
- industrial gas turbine engine 10 is a non-limiting embodiment and that a variety of other gas turbine engine configurations are also contemplated herein including, for example, gas turbine engines suitable for propulsion of aircraft including helicopters, airplanes, missiles, unmanned space devices and other similar devices, gas turbine engines suitable for pumping sets for oil and gas transmission lines, and as prime movers in a marine propulsion system.
- gas turbine engines suitable for propulsion of aircraft including helicopters, airplanes, missiles, unmanned space devices and other similar devices
- gas turbine engines suitable for pumping sets for oil and gas transmission lines and as prime movers in a marine propulsion system.
- the operation of gas turbine engines is considered conventional and will not be discussed further as it is believed known to one of ordinary skill in the art.
- combustor section 16 includes a number of combustion chambers, such as combustion chamber 28 which is illustrated generically in the cutaway portion of Fig. 1 .
- the combustor section 16 is a low emissions combustor system that utilizes the premixing of fuel and air to obtain a lean combustionable mixture which prevents the formation of harmful emissions.
- fuel and air are combusted in combustion chamber 28.
- air broadly refers to the full range of working fluids that may be utilized by gas turbine engines.
- the hot gaseous products of combustion pass to turbine sections 18 and 20 which drive other sections of gas turbine engine 10 and/or other loads, for example, those described above.
- gas turbine engine 10 is operable using gaseous and/or liquid fuel. In other embodiments gas turbine engine 10 is operable using only gaseous fuel or only liquid fuel.
- liquid fuels include kerosene and aviation fuel, and non-limiting examples of gaseous fuel include natural gas as well as other gaseous hydrocarbons.
- Premix injector 200 includes a fuel manifold 220 which is supplied with gaseous or liquid fuel by fuel inlet pipe 210 from a fuel supply (not illustrated). Fuel manifold 220 is substantially annular and is bordered by inner wall member 221 and middle wall member 223. Premix injector 200 further includes a fuel-air mixing duct 214 which is substantially annular and is bordered by middle wall member 223 and an outer wall member 225. A number of inlet slots 216 in outer wall member 225 allow air to flow into fuel air mixing duct 214 as is indicated by arrows A.
- a plurality of circumferentially spaced gaseous fuel inlet apertures 222 in middle wall member 223 allow gaseous fuel to enter fuel air mixing duct 214 as is indicated by arrows G, and a plurality of liquid fuel inlet apertures 224 in middle wall member 223 allow liquid fuel to enter fuel air mixing duct 214 as is indicated by arrows L.
- the fuel-air mixture flows through fuel air mixing duct 214 toward a plurality of spaced apart vanes 218 which divide the fuel air mixing duct 214 into a plurality of discrete outlet flow paths.
- the flowing fuel air mixture is divided into a number of discrete outlet flow streams of the fuel air mixture.
- the vanes 218 reduce the exit area of the fuel-air mixing duct 214 prior to the combustor and accelerated flow to prevent flashback.
- the vanes 218 are preferably of an aerodynamic shape, however, other shapes and structures at the exit area of the fuel-air mixing duct 214 are contemplated herein.
- the present description utilizes the term vane to cover aerodynamic and non-aerodynamic structures unless specifically provided to the contrary.
- Each outlet flow stream exits premix injector 200 through an outlet window leading to combustion chamber 250 where combustion occurs as a number of discrete flames 246.
- Flames 246 are stabilized by recirculation zone 228 intermediate each flame, by recirculation zone 248 in the central region of the combustion chamber, and by recirculation zone 238 around the periphery of flames 246. Vanes 218 direct and accelerate flow exiting premix injector 200.
- Flames 246 are preferably discrete regions of combustion having a substantially elongate cone shape. The elongate cone shape results in a relatively large flame area which contributes to a more rapid and complete combustion process.
- the fuel air mixture exiting the premix injector 200 is preferably a lean combustible mixture.
- the number and position of fuel inlet apertures may vary from the illustrated embodiments.
- the gaseous fuel inlet apertures are located along the length of the inlet slots, most preferably in the bottom two thirds of the length of the inlet slots.
- the liquid fuel inlet apertures are located downstream from the inlet slots in the region between vanes. Further embodiments contemplate different shapes, numbers, locations and arrangements of fuel inlet apertures.
- premix injector 200 taken along line 3-3 in Fig. 2 .
- air flowing into fuel air mixing duct 214 from inlet slots 216 forms a pair of vortex flows which flow from inlet slots 216 toward vanes 218.
- Inlet slots 216 extend along a portion of the axial length of premix injector 200 and preferably admit air flow in a substantially radial or perpendicular direction.
- the inlet slots 216 extend along the direction of flow within the fuel air mixing duct 214.
- Inlet slots 216 are illustrated as having a generally rectangular shape; however, they may also have other shapes, for example, a tapered shape having greater width toward vanes 218.
- Inlet slots 216 have a length 310 which is preferably selected to satisfy the inequality fL U ⁇ 1 where f is the frequency of the lowest acoustic mode of a combustion chamber to which premix injector 200 is fluidly coupled, L is slot length, and U is the average velocity of air in the fuel air mixing duct 214 at the point of inlet slot termination, which is located at the end of the inlet slot closest to vanes 218. Inlet slots 216 are spaced apart by a distance 320. The configuration of inlet slots 216, fuel inlet apertures 222, 224 and vanes 218 continues about premix injector 200. It should be appreciated that a variety of numbers of inlet slots and associated vanes, and discharge windows are contemplated.
- each of the vanes acts as a flame holder and functions to stabilize the flame from all four sides of the window.
- jets of gaseous fuel enter fuel air mixing duct 214 through gaseous fuel inlet apertures 222 and are rapidly mixed with the vortex flow.
- the rapid mixing of the fuel and air is in the sub-millisecond range, however other mixing times are contemplated herein.
- L jets of liquid fuel enter fuel air mixing duct 214 through liquid fuel inlet apertures 224 and are rapidly atomized and mixed with the vortex flow. Mixing of the liquid fuel preferably involves airblast atomization to break up and disperse fuel droplets.
- the size and location of the liquid fuel apertures are preferably selected so that that liquid fuel jets exiting the apertures satisfy the inequality ( We )( MFR ) 5/4 ⁇ 8000 where We is the Weber number based on the diameter of the liquid fuel jet and MFR is the momentum flux ratio of the liquid fuel jet.
- the location of the liquid fuel inlet aperture is where the fluid flowing within the fuel air mixing duct has a velocity greater than 50 meters/second.
- the mixture of fuel and air exits premix injector 200 at windows 220 which are located intermediate vanes 218.
- exit windows 220 provide flow to a number of discrete flames 246 located intermediate recirculation flows 228.
- Fig. 3 applies to each of the inlet slots 216, gaseous fuel inlet apertures 222, liquid fuel inlet apertures 224, vanes and windows 220 of premix injector 200, although certain features are illustrated for only certain inlet slots 216, gaseous fuel inlet apertures 222, liquid fuel inlet apertures 224, vanes, or windows 220 for the sake of clarity and simplicity.
- Fig. 4 there is illustrated a portion of premix injector 200 taken along line 4-4 in Fig. 3 .
- a air flow enters fuel air mixing duct 214 through inlet slots 216 to produce pairs of vortex flow indicated by arrows V.
- the pair of vortex flow is counter rotating and result in very rapid mixing of the fuel and air.
- the vortex flow defines streamwise vortices that are used for flame stabilization within the combustion chamber.
- the distance 320 between inlet slots 216 is preferably selected to be between 1.5 to 3 times the height 330 of fuel air mixing duct 214. In one embodiment the distance 320 between inlet slots 216 is approximately 2 times the height 330 of fuel air missing duct 214. However, other distances between the inlet slots are contemplated herein.
- the primary stage of the premix injector 500 includes in one embodiment a substantially annular primary fuel manifold 512 to which gaseous or liquid fuel is supplied via a primary fuel supply pipe 510.
- Primary fuel supply pipe 510 is in flow communication with a fuel source (not illustrated).
- the primary stage of premix injector 500 includes a substantially annular primary air-fuel mixing duct 514.
- Gaseous fuel enters primary air-fuel mixing duct 514 through primary gaseous fuel inlet apertures 522 as indicated by arrows G.
- Liquid fuel enters primary air-fuel mixing duct 514 through primary liquid fuel inlet apertures 524 as indicated by arrows L.
- Inlet slots 516 allow air to flow into duct 514 as indicated by arrows A. As was described above in connection with Figs. 2-4 , inlet slots 516 produce vortex flows in primary air-fuel mixing duct 514 which contribute to fuel-air mixing.
- the characteristics and dimensions of inlet slots 516, primary gaseous fuel inlet apertures 522, primary liquid fuel inlet apertures 524 and other features of the primary stage of premix injector 500 can be designed the same or similar to those of inlet slots 216, gaseous fuel inlet apertures 222, liquid fuel inlet aperture 224 and other features of premix injector 200 discussed above in connection with Figs. 2-4 .
- the air fuel mixture flows through primary air-fuel mixing duct 514 to vanes 518 which direct the flow through discharge windows 520 which are located intermediate vanes 518.
- the secondary stage of premix injector 500 includes a secondary fuel manifold 532 to which gaseous or liquid fuel is supplied via secondary fuel supply pipe 530.
- the secondary stage of premix injector 500 includes a substantially annular secondary air-fuel mixing duct 534.
- Gaseous fuel enters secondary air-fuel mixing duct 534 through secondary gaseous fuel inlet apertures 542 as indicated by arrows GG.
- Liquid fuel enters secondary air-fuel mixing duct 534 through secondary liquid fuel inlet apertures 544 as indicated by arrows LL.
- inlet slots 536 produce vortex flows in secondary air-fuel mixing duct 534 which contribute to fuel-air mixing.
- the characteristics and dimensions of inlet slots 536, secondary gaseous fuel inlet apertures 542, secondary liquid fuel inlet apertures 544 and other features of the secondary stage of premix injector 500 can be the same or similar to those of inlet slots 216, gaseous fuel inlet apertures 222, liquid fuel inlet apertures 224 and other features of premix injector 200 discussed above in connection with Figs. 2-4 .
- the air-fuel mixture flows through secondary air fuel mixing duct 534 to vanes 538 which direct the fluid flow through discharge windows 540 which are located intermediate vanes 538.
- FIG. 6 there is illustrated a perspective view of premix injector 500.
- discharge windows 540 are located radially inward from and axially downstream from discharge windows 520
- FIG. 7 there is illustrated a perspective partial cutaway view of premix injector 500.
- vanes 518 and 538 are angled to impart an overall swill to the output of discharge windows 520 and 540, respectively, and are angled outward from the axial centerline of premix injector 500 to be diverging from one another.
- Combustor section 800 includes casing 810, and inlet 820 which supplies compressed air from the compressor section. Compressed air and fuel are provided to premix injector 500 as described above.
- Combustor liner 850 defines combustion chamber 590 in which primary flames 591 and secondary flames 592 combust a fuel-air mixture from premix injector 500.
- Fig. 8 illustrates a silo type combustion chamber. It should be appreciated, however, that a variety of other types of combustion chambers are contemplated, including can type, annular type, and can-annular type combustions chambers as well as others. The present application contemplates the agility to control fuel delivery to the entire premix injector or sub-portions thereof.
Description
- The technical field relates generally to gas turbine engine fuel injectors, and more particularly, but not exclusively, to premix injectors for industrial gas turbine engines.
- Gas turbine engines are an efficient source of useful energy and have proven reliable for electricity generation, as well as for other uses. Gas turbine engines may include premix injectors for providing a mixture of air and fuel for combustion. Many gas turbine engine premix injectors suffer from a number limitations, and drawbacks, for example, those respecting size, complexity, part commit, emissions, and others. Thus, there is a need for the unique and inventive premix injectors disclosed herein.
-
EP1321715 discloses an improved combination of a premixing chamber and a combustion chamber, with low emission of pollutants, for gas turbines running on liquid and/or gas fuel, in which the combustion chamber has a truncated conical end a and is surrounded by a cavity for cooling air, the cavity carrying combustion air to the premixing chamber, which has at its inlet apertures or ports which can be constricted according to the quantity of fuel used, and at its outlet a circumferential set of burners to create a corresponding set of additional flames. Gas fuel supply means and liquid fuel injection devices are provided in the premixing chamber, and a set of liquid fuel injectors is present on the end. - According to an aspect of the invention there is provided a gas turbine premix injector as set out in claim 1.
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Fig. 1 is a schematic representation of one embodiment of a gas turbine engine. -
Fig. 2 is sectional view of one embodiment of a premix injector, a combustion chamber, and a combustion reaction within the chamber. -
Fig. 3 is a view of a portion ofFig. 2 taken along line 3-3 inFig. 2 . -
Fig. 4 is a view of a portion ofFig. 3 taken along line 4-4 inFig. 3 . -
Fig. 5 is a sectional view of one embodiment of a premix injector. -
Fig. 6 is a perspective view of the premix injector ofFig. 5 . -
Fig. 7 is a perspective, partial cutaway view of the premix injector ofFig. 5 . -
Fig. 8 is a sectional view of one embodiment of a gas turbine engine combustor section including the premix injector ofFig. 5 . - For the purposes of promoting an understanding of the principles of the invention, reference will now be made to the embodiment illustrated in the drawings and specific language will be used to describe the same. It will nevertheless be understood that no limitation of the scope of the invention is thereby intended, such alterations and further modifications in the illustrated device, and such further applications of the principles of the invention as illustrated therein being contemplated as would normally occur to one skilled in the art to which the invention relates.
- With reference to
Fig. 1 , there is illustrated an industrialgas turbine engine 10, including, aninlet 12, acompressor section 14, acombustor section 16, aturbine section 18, apower turbine section 20 and anexhaust 22.Turbine section 18 is arranged to drive thecompressor section 14 andpower turbine section 20 drives anelectrical generator 26 via ashaft 24. Furthermore,power turbine section 20 may be arranged to provide drive for other applications. It should be understood that industrialgas turbine engine 10 is a non-limiting embodiment and that a variety of other gas turbine engine configurations are also contemplated herein including, for example, gas turbine engines suitable for propulsion of aircraft including helicopters, airplanes, missiles, unmanned space devices and other similar devices, gas turbine engines suitable for pumping sets for oil and gas transmission lines, and as prime movers in a marine propulsion system. The operation of gas turbine engines is considered conventional and will not be discussed further as it is believed known to one of ordinary skill in the art. - With continuing reference to
Fig. 1 ,combustor section 16 includes a number of combustion chambers, such ascombustion chamber 28 which is illustrated generically in the cutaway portion ofFig. 1 . In one form thecombustor section 16 is a low emissions combustor system that utilizes the premixing of fuel and air to obtain a lean combustionable mixture which prevents the formation of harmful emissions. During operation ofgas turbine engine 10, fuel and air are combusted incombustion chamber 28. It should be understood that the term air broadly refers to the full range of working fluids that may be utilized by gas turbine engines. The hot gaseous products of combustion pass toturbine sections gas turbine engine 10 and/or other loads, for example, those described above. In one embodiment,gas turbine engine 10 is operable using gaseous and/or liquid fuel. In other embodimentsgas turbine engine 10 is operable using only gaseous fuel or only liquid fuel. Non-limiting examples of liquid fuels include kerosene and aviation fuel, and non-limiting examples of gaseous fuel include natural gas as well as other gaseous hydrocarbons. - With reference to
Fig. 2 , there is illustrated one embodiment of apremix injector 200. Premixinjector 200 includes afuel manifold 220 which is supplied with gaseous or liquid fuel byfuel inlet pipe 210 from a fuel supply (not illustrated).Fuel manifold 220 is substantially annular and is bordered byinner wall member 221 andmiddle wall member 223. Premixinjector 200 further includes a fuel-air mixing duct 214 which is substantially annular and is bordered bymiddle wall member 223 and anouter wall member 225. A number ofinlet slots 216 inouter wall member 225 allow air to flow into fuelair mixing duct 214 as is indicated by arrows A. A plurality of circumferentially spaced gaseousfuel inlet apertures 222 inmiddle wall member 223 allow gaseous fuel to enter fuelair mixing duct 214 as is indicated by arrows G, and a plurality of liquidfuel inlet apertures 224 inmiddle wall member 223 allow liquid fuel to enter fuelair mixing duct 214 as is indicated by arrows L. - Fuel enters fuel
air mixing duct 214 and mixes with air flowing therein. The fuel-air mixture flows through fuelair mixing duct 214 toward a plurality of spaced apartvanes 218 which divide the fuelair mixing duct 214 into a plurality of discrete outlet flow paths. The flowing fuel air mixture is divided into a number of discrete outlet flow streams of the fuel air mixture. - The
vanes 218 reduce the exit area of the fuel-air mixing duct 214 prior to the combustor and accelerated flow to prevent flashback. Thevanes 218 are preferably of an aerodynamic shape, however, other shapes and structures at the exit area of the fuel-air mixing duct 214 are contemplated herein. The present description utilizes the term vane to cover aerodynamic and non-aerodynamic structures unless specifically provided to the contrary. - Each outlet flow stream
exits premix injector 200 through an outlet window leading tocombustion chamber 250 where combustion occurs as a number ofdiscrete flames 246.Flames 246 are stabilized byrecirculation zone 228 intermediate each flame, byrecirculation zone 248 in the central region of the combustion chamber, and byrecirculation zone 238 around the periphery offlames 246. Vanes 218 direct and accelerate flow exitingpremix injector 200. Flames 246 are preferably discrete regions of combustion having a substantially elongate cone shape. The elongate cone shape results in a relatively large flame area which contributes to a more rapid and complete combustion process. The fuel air mixture exiting thepremix injector 200 is preferably a lean combustible mixture. - The number and position of fuel inlet apertures may vary from the illustrated embodiments. Preferably, the gaseous fuel inlet apertures are located along the length of the inlet slots, most preferably in the bottom two thirds of the length of the inlet slots. There can be more than one gaseous fuel aperture located along the length of each inlet slot or in the spaces between inlet slots. Preferably, the liquid fuel inlet apertures are located downstream from the inlet slots in the region between vanes. Further embodiments contemplate different shapes, numbers, locations and arrangements of fuel inlet apertures.
- With reference to
Fig. 3 , there is illustrated a portion ofpremix injector 200 taken along line 3-3 inFig. 2 . As indicated by arrows A, air flowing into fuelair mixing duct 214 frominlet slots 216 forms a pair of vortex flows which flow frominlet slots 216 towardvanes 218.Inlet slots 216 extend along a portion of the axial length ofpremix injector 200 and preferably admit air flow in a substantially radial or perpendicular direction. Theinlet slots 216 extend along the direction of flow within the fuelair mixing duct 214.Inlet slots 216 are illustrated as having a generally rectangular shape; however, they may also have other shapes, for example, a tapered shape having greater width towardvanes 218.Inlet slots 216 have alength 310 which is preferably selected to satisfy the inequalitypremix injector 200 is fluidly coupled, L is slot length, and U is the average velocity of air in the fuelair mixing duct 214 at the point of inlet slot termination, which is located at the end of the inlet slot closest tovanes 218.Inlet slots 216 are spaced apart by adistance 320. The configuration ofinlet slots 216,fuel inlet apertures vanes 218 continues aboutpremix injector 200. It should be appreciated that a variety of numbers of inlet slots and associated vanes, and discharge windows are contemplated. Preferably, there are six or more discharge windows and associated vanes, and inlet slots. In one form each of the vanes acts as a flame holder and functions to stabilize the flame from all four sides of the window. In certain embodiments there are as many as twenty to fifty or more discharge windows and associated vanes and inlet slots. In one form there is included a discharge window for each inlet slot. - As indicated by arrows G, jets of gaseous fuel enter fuel
air mixing duct 214 through gaseousfuel inlet apertures 222 and are rapidly mixed with the vortex flow. In one form the rapid mixing of the fuel and air is in the sub-millisecond range, however other mixing times are contemplated herein. As indicated by arrows L jets of liquid fuel enter fuelair mixing duct 214 through liquidfuel inlet apertures 224 and are rapidly atomized and mixed with the vortex flow. Mixing of the liquid fuel preferably involves airblast atomization to break up and disperse fuel droplets. The size and location of the liquid fuel apertures are preferably selected so that that liquid fuel jets exiting the apertures satisfy the inequality (We)(MFR)5/4 ≥ 8000 where We is the Weber number based on the diameter of the liquid fuel jet and MFR is the momentum flux ratio of the liquid fuel jet. In one non-limiting embodiment the location of the liquid fuel inlet aperture is where the fluid flowing within the fuel air mixing duct has a velocity greater than 50 meters/second. - As indicated by arrows M, the mixture of fuel and air exits
premix injector 200 atwindows 220 which are locatedintermediate vanes 218. During combustion,exit windows 220 provide flow to a number ofdiscrete flames 246 located intermediate recirculation flows 228. It should be appreciated that the description ofFig. 3 applies to each of theinlet slots 216, gaseousfuel inlet apertures 222, liquidfuel inlet apertures 224, vanes andwindows 220 ofpremix injector 200, although certain features are illustrated for onlycertain inlet slots 216, gaseousfuel inlet apertures 222, liquidfuel inlet apertures 224, vanes, orwindows 220 for the sake of clarity and simplicity. - With reference to
Fig. 4 , there is illustrated a portion ofpremix injector 200 taken along line 4-4 inFig. 3 . As indicated by arrows A air flow enters fuelair mixing duct 214 throughinlet slots 216 to produce pairs of vortex flow indicated by arrows V. The pair of vortex flow is counter rotating and result in very rapid mixing of the fuel and air. In one form the vortex flow defines streamwise vortices that are used for flame stabilization within the combustion chamber. Thedistance 320 betweeninlet slots 216 is preferably selected to be between 1.5 to 3 times theheight 330 of fuelair mixing duct 214. In one embodiment thedistance 320 betweeninlet slots 216 is approximately 2 times theheight 330 of fuelair missing duct 214. However, other distances between the inlet slots are contemplated herein. - With reference to
Fig. 5 , there is illustrated one embodiment of a twostage premix injector 500. The primary stage of thepremix injector 500 includes in one embodiment a substantially annularprimary fuel manifold 512 to which gaseous or liquid fuel is supplied via a primaryfuel supply pipe 510. Primaryfuel supply pipe 510 is in flow communication with a fuel source (not illustrated). The primary stage ofpremix injector 500 includes a substantially annular primary air-fuel mixing duct 514. Gaseous fuel enters primary air-fuel mixing duct 514 through primary gaseousfuel inlet apertures 522 as indicated by arrows G. Liquid fuel enters primary air-fuel mixing duct 514 through primary liquidfuel inlet apertures 524 as indicated by arrowsL. Inlet slots 516 allow air to flow intoduct 514 as indicated by arrows A. As was described above in connection withFigs. 2-4 ,inlet slots 516 produce vortex flows in primary air-fuel mixing duct 514 which contribute to fuel-air mixing. The characteristics and dimensions ofinlet slots 516, primary gaseousfuel inlet apertures 522, primary liquidfuel inlet apertures 524 and other features of the primary stage ofpremix injector 500 can be designed the same or similar to those ofinlet slots 216, gaseousfuel inlet apertures 222, liquidfuel inlet aperture 224 and other features ofpremix injector 200 discussed above in connection withFigs. 2-4 . The air fuel mixture flows through primary air-fuel mixing duct 514 tovanes 518 which direct the flow throughdischarge windows 520 which are locatedintermediate vanes 518. - The secondary stage of
premix injector 500 includes asecondary fuel manifold 532 to which gaseous or liquid fuel is supplied via secondaryfuel supply pipe 530. The secondary stage ofpremix injector 500 includes a substantially annular secondary air-fuel mixing duct 534. Gaseous fuel enters secondary air-fuel mixing duct 534 through secondary gaseousfuel inlet apertures 542 as indicated by arrows GG. Liquid fuel enters secondary air-fuel mixing duct 534 through secondary liquidfuel inlet apertures 544 as indicated by arrows LL. Air flows to secondaryair inlet passage 526 as indicated by arrows I, andinlet slots 536 allow air to flow into secondary air-fuel mixing duct 534 as indicated by arrows AA. As was described above in connection withFigs. 2-4 ,inlet slots 536 produce vortex flows in secondary air-fuel mixing duct 534 which contribute to fuel-air mixing. The characteristics and dimensions ofinlet slots 536, secondary gaseousfuel inlet apertures 542, secondary liquidfuel inlet apertures 544 and other features of the secondary stage ofpremix injector 500 can be the same or similar to those ofinlet slots 216, gaseousfuel inlet apertures 222, liquidfuel inlet apertures 224 and other features ofpremix injector 200 discussed above in connection withFigs. 2-4 . The air-fuel mixture flows through secondary airfuel mixing duct 534 tovanes 538 which direct the fluid flow throughdischarge windows 540 which are locatedintermediate vanes 538. - With reference to
Fig. 6 , there is illustrated a perspective view ofpremix injector 500. In the illustratedembodiment discharge windows 540 are located radially inward from and axially downstream fromdischarge windows 520, With reference toFig. 7 , there is illustrated a perspective partial cutaway view ofpremix injector 500. In the illustrated embodiment,vanes discharge windows premix injector 500 to be diverging from one another. - With reference to
Fig. 8 there is illustrated an exemplary embodiment of a gas turbineengine combustor section 800 includingpremix injector 500 which was described above.Combustor section 800 includescasing 810, andinlet 820 which supplies compressed air from the compressor section. Compressed air and fuel are provided to premixinjector 500 as described above.Combustor liner 850 definescombustion chamber 590 in whichprimary flames 591 andsecondary flames 592 combust a fuel-air mixture frompremix injector 500.Fig. 8 illustrates a silo type combustion chamber. It should be appreciated, however, that a variety of other types of combustion chambers are contemplated, including can type, annular type, and can-annular type combustions chambers as well as others. The present application contemplates the agility to control fuel delivery to the entire premix injector or sub-portions thereof. - While the invention has been illustrated and described in detail in the drawings and foregoing description, the same is to be considered as illustrative and not restrictive in character, it being understood that only the preferred embodiments have been shown and described and that all changes and modifications that come within the scope of the claims are desired to be protected. It should be understood that while the use of words such as preferable, preferably, preferred or more preferred utilized in the description above indicate that the feature so described may be more desirable, it nonetheless may not be necessary and embodiments lacking the same may be contemplated as within the scope of the invention, the scope being defined by the claims that follow. In reading the claims, it is intended that when words such as "a," "an," "at least one," or "at least one portion" are used there is no intention to limit the claim to only one item unless specifically stated to the contrary in the claim. When the language "at least a portion" and/or "a portion" is used the item can include a portion and/or the entire item unless specifically stated to the contrary.
Claims (14)
- A gas turbine premix injector (200, 500) comprising:a mixing duct (214, 514, 534);a plurality of air inlet slots (216, 516, 536) leading to said mixing duct;a plurality of gaseous fuel inlet apertures (222, 522, 542) leading to said mixing duct;a plurality of members positioned in said mixing duct (214, 514, 534) downstream from said plurality of air inlet slots (216, 516, 536) for dividing fluid flow within said mixing duct; anda plurality of liquid fuel inlet apertures (224, 524, 544) leading to said mixing duct; andcharacterized in that
said air inlet slots (216, 516, 536) are formed in a first surface of said mixing duct (214, 514, 534), said gaseous fuel inlet apertures (222, 522, 542) are formed in a second surface of said mixing duct opposite said first surface, said first surface and said second surface forming an annular space defined between walls having the first surface and second surface downstream of the plurality of air inlet slots (216, 516, 536). - The injector of claim 1 wherein said plurality of members define a plurality of vanes (218, 518, 538).
- The injector of claim 1 or claim 2 wherein said mixing duct (214, 514, 534) is substantially annular and the ratio of distance between adjacent slots to height of the mixing duct is between 1.5 and 3.
- The injector of any preceding claim, wherein the length of each of said slots (216, 516, 536) satisfies
- The injector of any preceding claim, wherein said liquid fuel inlet apertures (222, 522, 542) are positioned to direct a fuel jet intermediate pairs of said plurality of members.
- The injector of any preceding claim wherein each of said plurality of air inlet slots (216, 516, 536) providing a vortex flow to said mixing duct (214, 514, 534);
and which further includes a first plurality of discharge windows (220, 520), - The injector of claim 6 , further comprising a second plurality of discharge windows (540) positioned radially inward from and downstream from said first plurality of discharge windows.
- The injector of any one of claims 6 or 7, wherein each of said inlet slots (216, 516, 536) generates two vortex flows within said mixing duct (214, 514, 534).
- The injector of any one of claims 1-5 which further includes a plurality of discharge windows (220, 520, 540), each discharge window suitable to provide a lean combustible fluid flow to a discrete flame associated with each window such that a plurality of discrete flames are formed.
- The injector of any of claims 6-9, further comprising a plurality of means for mixing fuel and air.
- The injector of claims 6-10, further comprising a plurality of means for routing flow to said discharge windows (220, 520, 540).
- The injector of any one of claims 6-11, further comprising a plurality of means for providing a lean combustible mixture of liquid fuel and air.
- An assembly comprising the injector of any one of claims 6-12, and a combustion chamber (250, 590) in flow communication with said discharge windows (220, 520, 540).
- A gas turbine engine combustor section comprising a premix injector (200, 500) according to any preceding claim.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US75016805P | 2005-12-14 | 2005-12-14 | |
PCT/IB2006/004251 WO2007119115A2 (en) | 2005-12-14 | 2006-12-14 | Gas turbine engine premix injectors |
Publications (3)
Publication Number | Publication Date |
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EP2041494A2 EP2041494A2 (en) | 2009-04-01 |
EP2041494B1 true EP2041494B1 (en) | 2015-02-18 |
EP2041494B8 EP2041494B8 (en) | 2015-05-27 |
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Family Applications (1)
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EP06850471.1A Active EP2041494B8 (en) | 2005-12-14 | 2006-12-14 | Gas turbine engine premix injectors |
Country Status (4)
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US (1) | US8881531B2 (en) |
EP (1) | EP2041494B8 (en) |
CA (1) | CA2630721C (en) |
WO (1) | WO2007119115A2 (en) |
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- 2006-12-14 EP EP06850471.1A patent/EP2041494B8/en active Active
- 2006-12-14 CA CA2630721A patent/CA2630721C/en active Active
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US20070151248A1 (en) | 2007-07-05 |
CA2630721A1 (en) | 2007-10-25 |
EP2041494A2 (en) | 2009-04-01 |
WO2007119115A3 (en) | 2009-03-12 |
US8881531B2 (en) | 2014-11-11 |
WO2007119115A2 (en) | 2007-10-25 |
CA2630721C (en) | 2012-06-19 |
EP2041494B8 (en) | 2015-05-27 |
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